CN115127770B - Wind tunnel test device for simulating pneumatic ablation injection effect - Google Patents
Wind tunnel test device for simulating pneumatic ablation injection effect Download PDFInfo
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- CN115127770B CN115127770B CN202210772270.9A CN202210772270A CN115127770B CN 115127770 B CN115127770 B CN 115127770B CN 202210772270 A CN202210772270 A CN 202210772270A CN 115127770 B CN115127770 B CN 115127770B
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- 238000002679 ablation Methods 0.000 title claims abstract description 50
- 238000012360 testing method Methods 0.000 title claims abstract description 26
- 230000000694 effects Effects 0.000 title claims abstract description 16
- 238000002347 injection Methods 0.000 title abstract description 20
- 239000007924 injection Substances 0.000 title abstract description 20
- 238000009423 ventilation Methods 0.000 claims abstract description 27
- 239000000463 material Substances 0.000 claims abstract description 21
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 15
- 239000010959 steel Substances 0.000 claims abstract description 15
- 238000005192 partition Methods 0.000 claims abstract description 13
- 230000001105 regulatory effect Effects 0.000 claims abstract description 11
- 238000007789 sealing Methods 0.000 claims abstract description 8
- 239000007789 gas Substances 0.000 claims description 34
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 4
- 239000001307 helium Substances 0.000 claims description 2
- 229910052734 helium Inorganic materials 0.000 claims description 2
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 claims description 2
- 229910052754 neon Inorganic materials 0.000 claims description 2
- GKAOGPIIYCISHV-UHFFFAOYSA-N neon atom Chemical compound [Ne] GKAOGPIIYCISHV-UHFFFAOYSA-N 0.000 claims description 2
- 229910052757 nitrogen Inorganic materials 0.000 claims description 2
- 230000035699 permeability Effects 0.000 abstract description 7
- 230000009471 action Effects 0.000 abstract description 5
- 238000011160 research Methods 0.000 abstract description 5
- 239000000203 mixture Substances 0.000 abstract description 4
- 238000000034 method Methods 0.000 description 11
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 239000011148 porous material Substances 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 239000012466 permeate Substances 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 238000000859 sublimation Methods 0.000 description 1
- 230000008022 sublimation Effects 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
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- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a wind tunnel test device for simulating pneumatic ablation injection action, which comprises: the device comprises a ventilation model, a model base, a supporting rod, a model inner cavity partition plate, a sealing gasket, an upper air channel, a lower air channel, a tensioning screw, a flowmeter, a pressure gauge and a pressure regulating valve. The model, the model base and the model cavity partition board jointly form an upper cavity and a lower cavity of the model, and air is supplied through an upper air channel and a lower air channel respectively. After air supply, the air in the inner cavity of the model seeps out of the surface of the model through the air-permeable steel model, so that the purpose of simulating the ejection effect of the ablation air is achieved. Aiming at the actual ablation ejection situation of a research object, the aim of simulating the ablation ejection effect of the surface position of the whole or different models can be achieved by adjusting or changing the gas composition of the gas source, the pressure and flow of the gas source, the air permeability of the model air permeable material and the wall thickness of the model.
Description
Technical Field
The invention relates to a wind tunnel test device for simulating pneumatic ablation injection action, and belongs to the field of test aerodynamics.
Background
The reentry vehicle generates a pneumatic ablation during reentry into the atmosphere. The surface ablative material of the aircraft is subjected to intense heating by external air friction, physical changes such as decomposition, melting, evaporation, sublimation and the like and chemical reactions with surrounding air, the surface of the material is subjected to larger mass loss and mixed into a boundary layer, and the ejection effect can change the thickness of the boundary layer and influence the aerodynamic characteristics of the aircraft.
Wind tunnel test researches aiming at the pneumatic ablation effect of the reentry aircraft mainly obtain the variation results of the ablation appearance and the ablation surface morphology. If an arc heater or a gas flow device is used for carrying out a high-temperature ablation test, obtaining a pneumatic ablation result of an ablated material in the real flight of the aircraft; or a low-temperature ablation material is adopted in a hypersonic wind tunnel to simulate an ablation process, and the influence of aerodynamic parameters on the ablation appearance and the ablation surface morphology is focused. The research purpose of the test methods is to obtain the ablation appearance and the surface morphology change result of the reentrant aircraft, and the ejection effect of the mass loss and the mixed boundary layer of the ablated material after the air friction in the ablation process cannot be simulated.
Disclosure of Invention
The invention solves the technical problems that: the wind tunnel test device can simulate the pneumatic ablation injection action of the reentry vehicle.
The technical solution of the invention is as follows:
A wind tunnel test device for simulating pneumatic ablation ejection, comprising: the device comprises a ventilation model, a supporting rod, a model inner cavity partition board and a pipeline;
one end of the supporting rod is fixedly connected with the tail part of the ventilation model, so that a cone-shaped cavity is formed in the ventilation model;
the model inner cavity partition board is arranged in the conical cavity body, so that the conical cavity body is divided into two cavities;
Two air passage channels which are respectively communicated with different cavities are arranged in the support rod;
the other end of the supporting rod is fixedly connected with a pipeline which is used for conveying a gas medium;
Two ends of the air channel are respectively communicated with the pipeline and the cavity;
the material of the gas permeable pattern is capable of allowing the gaseous medium in the cavity to seep outwards.
Preferably, the wall thickness of the gas permeable pattern increases with increasing inner diameter.
Preferably, the inner cavity partition plate of the model is fixedly connected with the supporting rod or is integrally processed with the supporting rod.
Preferably, the method further comprises: a sealing gasket;
a sealing gasket is arranged between the inner cavity partition plate of the model and the ventilation model for sealing.
Preferably, the method further comprises: tightening the screw;
The tail part of the ventilation model is fixedly connected with the supporting rod through a tensioning screw.
Preferably, the method further comprises: a flow meter; for detecting the flow of the gaseous medium in the pipeline.
Preferably, the method further comprises: a pressure gauge; for detecting the pressure of the gaseous medium in the pipeline.
Preferably, the method further comprises: a pressure regulating valve; for adjusting the pressure of the gaseous medium in the pipeline.
Preferably, the gaseous medium is any one of air, nitrogen, neon or helium.
Preferably, the material of the gas permeable mould is a gas permeable steel material.
Compared with the prior art, the invention has the following advantages:
(1) The invention can simulate the gas injection effect that the surface ablation material of the aircraft is rubbed by external air, decomposed, melted, evaporated, sublimated or chemically reacted and mixed into a boundary layer during the reentry and ablation process of the reentry aircraft.
(2) The invention can perform more realistic ablation ejection simulation aiming at the actual ablation ejection situation of the research object. The gas composition, the gas pressure, the flow, the air permeability of the model air permeable material and the wall thickness of the model are regulated, so that the purpose of simulating the ablation injection effect of the whole or different model surface positions is achieved.
Drawings
Fig. 1 is a schematic structural view of the present invention.
FIG. 2 is a schematic illustration of a wind tunnel verification test pattern.
Detailed Description
The invention relates to a wind tunnel test device for simulating pneumatic ablation injection action, which mainly comprises two parts: a model-strut body portion and an external air path portion. The breathable steel material model is arranged on the model base and the supporting rod to form an internal cavity. After the gas circuit supplies gas, the pressure difference is formed between the inner cavity of the model and the outer part of the model, and the gas seeps out to the surface of the model through the gas-permeable steel model, so that the aim of simulating the ejection effect of the ablation gas is fulfilled. The specific implementation mode is as follows:
as shown in fig. 1, the structure of the present invention includes: the air-permeable model 1, the support rod 3, the model inner cavity partition plate 4, the sealing gasket 5, the upper and lower air passages 8, the tensioning screw B-1, the flowmeter W-1, the pressure gauge W-2 and the pressure regulating valve W-3.
The ventilation model 1 is made of ventilation steel, and the supporting rod 3 and the inner cavity partition plate 4 of the model are fixedly connected into a whole and made of steel. The end face of one end of the supporting rod 3 is provided with a model base 2, firstly, the equal-diameter section of the rear section of the ventilation model 1 is sleeved on the equal-diameter section of the front section of the model base 2, and then the ventilation model 1 is connected with the model base 2 by a tensioning screw B-1. The end face of the ventilation model 1 is provided with a unthreaded hole matched with a boss on the end face of the model base 2, and the unthreaded hole is in clearance fit with the boss.
And a conical cavity is formed between the ventilation model 1 and the model base 2 after the installation is completed. The model cavity baffle 4 is positioned in the middle of the model base 2 and equally divides the model cavity into an upper model cavity 6 and a lower model cavity 7. A sealing gasket 5 is embedded between the model inner cavity partition plate 4 and the ventilation model 1 and is used for preventing air flow intercommunication between the model upper inner cavity 6 and the model lower inner cavity 7 and ensuring that the model upper inner cavity 6 and the model lower inner cavity 7 are independent spaces. The inside of the supporting rod is communicated with an upper air channel 8 and a lower air channel 8, and can respectively supply air to the upper inner cavity 6 and the lower inner cavity 7 of the model.
The ventilation model 1 is made of ventilation steel, a certain pressure difference is formed between an upper inner cavity 6 of the model and a lower inner cavity 7 of the model after the air circuit supplies air and the outside of the model, and air in the upper inner cavity 6 of the model and the lower inner cavity 7 of the model can permeate out of the surface of the model through the ventilation steel ventilation model 1, so that the purpose of simulating the injection effect of ablative air is achieved. Different air paths are adopted in the upper inner cavity 6 and the lower inner cavity 7 of the model, so that the ablation ejection conditions of the upper surface and the lower surface of the ventilation model 1 can be conveniently simulated respectively. The wall thickness of the ventilation model 1 is different in the length direction and is used for adjusting the air permeability of different model positions and simulating the ablation ejection conditions of the surface positions of different models. The overall air permeability of the model air-permeable steel material is selected according to the ablation and ejection conditions of different study object models, and the air-permeable steel material can be of various types: PM-35-7, PM-35-25, PM-35-35.
The external air path is divided into an upper air path and a lower air path which are respectively connected with an upper air path and a lower air path 8 inside the supporting rod. After the gas circuit is connected with a gas source, a pressure regulating valve W-3 and a barometer W-2 are connected, and the pressure regulating valve W-3 is utilized to regulate the required gas flow pressure. And then the flow meter W-1 is connected for measuring the gas flow of the upper gas path and the lower gas path respectively, namely the air flow exudation mass flow of the upper surface and the lower surface of the model. The barometer W-2 is used to detect the pressure of the air flow of the air source. According to the ablation injection conditions of different research object models, gas components with different molecular weights or specific heat ratios can be selected as gas sources, and the gas sources can be adopted: air, N 2, ne, he, etc.
The working principle of the invention is as follows:
in the wind tunnel test environment, after the air supply of the air circuit, a certain pressure difference is formed between the inner cavity of the model and the outside, and air in the inner cavity of the model can permeate out of the surface of the model through the air-permeable steel die, so that the purpose of simulating the injection effect of ablative air is achieved. And observing and measuring the influence of the simulated ablation ejection effect on the boundary layer by using wind tunnel test measurement means such as schlieren, infrared heat map and the like.
According to different requirements of ablation injection of different study objects, the invention can adjust the ablation injection gas components and the total mass flow. The method and principle are as follows: the gas composition of the gas source is adjusted according to molecular weight or specific heat ratio, and gas compositions that may be used include, but are not limited to: air, N 2, ne, he; the model air-permeable steel material is selected according to air permeability, and air-permeable steel material models which can be used include but are not limited to: PM-35-7 (average pore size 7 μm), PM-35-25 (average pore size 25 μm), PM-35-35 (average pore size 35 μm);
Meanwhile, the invention can adjust the mass flow of the ablation injection gas of the windward side and the leeward side of the model and the surface positions of different models because of different ablation injection conditions of the different surface positions of the model. The method and principle are as follows: the inner cavity of the model is divided into an upper part and a lower part which are independent, and two paths of gas paths are adopted to simulate the ablation injection of the upper surface and the lower surface of the model (namely a windward surface and a leeward surface, for example, the model is a head-up attack angle, the upper surface is a leeward surface, and the lower surface is a windward surface) respectively; the pressure of the air flow is respectively regulated by an upper pressure regulating valve and a lower pressure regulating valve, so that the purpose of respectively regulating the mass flow of the air on the upper surface and the lower surface of the model is achieved; the wall thickness of the model is different in the length direction and is used for adjusting the air permeability of different model positions. As the air permeability of the air permeable steel material is inversely proportional to the thickness of the material, the mass flow of the ejected gas is larger at the thinner part of the wall thickness of the model, and vice versa, the purpose of simulating the ablation ejection effect of different model surface positions can be achieved.
The present invention is verified by wind tunnel test for specific examples. FIG. 2 shows the results of the test schlieren of the wind tunnel under the action of gas injection and no gas injection of a certain model, and the test Mach number is 6.0. Therefore, when gas injection exists, the thickness of the boundary layer on the surface of the model is obviously increased, and the simulation effect of the ablation gas injection is obvious.
Although the present application has been described in terms of the preferred embodiments, it is not intended to be limited to the embodiments, and any person skilled in the art can make any possible variations and modifications to the technical solution of the present application by using the methods and technical matters disclosed above without departing from the spirit and scope of the present application, so any simple modifications, equivalent variations and modifications to the embodiments described above according to the technical matters of the present application are within the scope of the technical matters of the present application. The embodiments of the present application and technical features in the embodiments may be combined with each other without collision.
What is not described in detail in the present specification is a well known technology to those skilled in the art.
Claims (10)
1. The wind tunnel test device for simulating the pneumatic ablation ejection effect is characterized by comprising: the device comprises a ventilation model (1), a supporting rod (3), a model inner cavity partition board (4) and a pipeline;
one end of the supporting rod (3) is fixedly connected with the tail part of the ventilation model (1) to enable the inside of the ventilation model (1) to form a cone-shaped cavity;
the model inner cavity partition board (4) is arranged in the conical cavity to divide the conical cavity into two cavities;
Two air passage channels which are respectively communicated with different cavities are arranged in the support rod (3);
The other end of the supporting rod (3) is fixedly connected with a pipeline which is used for conveying a gas medium;
Two ends of the air channel are respectively communicated with the pipeline and the cavity;
the material of the gas-permeable mould (1) is capable of allowing the gaseous medium in the cavity to exude outwards.
2. Wind tunnel test device simulating aerodynamic ablation ejection according to claim 1, characterized in that the wall thickness of the ventilation model (1) increases with increasing inner diameter.
3. The wind tunnel test device for simulating pneumatic ablation ejection according to claim 1, wherein the model inner cavity partition plate (4) is fixedly connected with the support rod (3) or is integrally processed with the support rod (3).
4. A wind tunnel test apparatus for simulating pneumatic ablation ejection as defined in claim 1, further comprising: a gasket (5);
a sealing gasket (5) is arranged between the inner cavity partition plate (4) of the model and the ventilation model (1) for sealing.
5. A wind tunnel test apparatus for simulating pneumatic ablation ejection as defined in claim 1, further comprising: tightening the screw (B-1);
the tail part of the ventilation model (1) is fixedly connected with the supporting rod (3) through a tensioning screw (B-1).
6. A wind tunnel test apparatus for simulating aerodynamic ablation ejection according to any one of claims 1 to 5, further comprising: a flowmeter (W-1); for detecting the flow of the gaseous medium in the pipeline.
7. A wind tunnel test apparatus for simulating aerodynamic ablation ejection according to any one of claims 1 to 5, further comprising: a pressure gauge (W-2); for detecting the pressure of the gaseous medium in the pipeline.
8. A wind tunnel test apparatus for simulating aerodynamic ablation ejection according to any one of claims 1 to 5, further comprising: a pressure regulating valve (W-3); for adjusting the pressure of the gaseous medium in the pipeline.
9. The wind tunnel test device for simulating pneumatic ablation ejection according to any one of claims 1 to 5, wherein the gaseous medium is any one of air, nitrogen, neon or helium.
10. A wind tunnel test device for simulating pneumatic ablation ejection according to any one of claims 1 to 5, wherein the material of the ventilation model (1) is a ventilation steel material.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210772270.9A CN115127770B (en) | 2022-06-30 | 2022-06-30 | Wind tunnel test device for simulating pneumatic ablation injection effect |
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| CN202210772270.9A CN115127770B (en) | 2022-06-30 | 2022-06-30 | Wind tunnel test device for simulating pneumatic ablation injection effect |
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| CN115127770B true CN115127770B (en) | 2024-06-11 |
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| CN115824575B (en) * | 2023-02-22 | 2023-04-18 | 中国空气动力研究与发展中心超高速空气动力研究所 | Test method for obtaining influence of model surface micro-jet on aerodynamic characteristics |
| CN116952526B (en) * | 2023-09-20 | 2023-12-05 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel ablation test model |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10206278A (en) * | 1997-01-21 | 1998-08-07 | Mitsubishi Heavy Ind Ltd | High-pressure-gas supply apparatus for wind-tunnel test model |
| US7401505B1 (en) * | 2007-01-09 | 2008-07-22 | The United States Of America As Represented By The Secretary Of The Navy | Low cost wind tunnel for supersonic and hypersonic aerothermal testing |
| CN209102324U (en) * | 2018-11-08 | 2019-07-12 | 中国航天空气动力技术研究院 | A kind of low temperature ablative modeling apparatus for hypersonic wind tunnel experiment |
| CN113390600A (en) * | 2021-07-26 | 2021-09-14 | 中国空气动力研究与发展中心计算空气动力研究所 | Shock tunnel test simulation device and method for pneumatic thermal effect of pyrolysis gas |
| CN113848032A (en) * | 2021-08-31 | 2021-12-28 | 中国航天空气动力技术研究院 | Two-side jet flow force measuring wind tunnel test device |
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- 2022-06-30 CN CN202210772270.9A patent/CN115127770B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10206278A (en) * | 1997-01-21 | 1998-08-07 | Mitsubishi Heavy Ind Ltd | High-pressure-gas supply apparatus for wind-tunnel test model |
| US7401505B1 (en) * | 2007-01-09 | 2008-07-22 | The United States Of America As Represented By The Secretary Of The Navy | Low cost wind tunnel for supersonic and hypersonic aerothermal testing |
| CN209102324U (en) * | 2018-11-08 | 2019-07-12 | 中国航天空气动力技术研究院 | A kind of low temperature ablative modeling apparatus for hypersonic wind tunnel experiment |
| CN113390600A (en) * | 2021-07-26 | 2021-09-14 | 中国空气动力研究与发展中心计算空气动力研究所 | Shock tunnel test simulation device and method for pneumatic thermal effect of pyrolysis gas |
| CN113848032A (en) * | 2021-08-31 | 2021-12-28 | 中国航天空气动力技术研究院 | Two-side jet flow force measuring wind tunnel test device |
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